Combustor assembly for a turbine engine
A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.
1. A combustor assembly for a gas turbine engine defining a centerline, an axial direction, and a radial direction, the combustor assembly comprising:
a dome defining a slot between a first inner surface of the dome, a second inner surface of the dome, and a forward surface of the dome;
a liner formed of a ceramic matrix composite (CMC) material and at least partially defining a combustion chamber, the liner extending between an aft end and a forward end thereof, the forward end of the liner configured to be received within the slot of the dome and comprising a liner opening, a radial interface surface, and an axial interface surface, the radial interface surface of the liner and the forward surface of the dome defining an axial gap therebetween, the axial interface surface of the liner and the first inner surface of the dome defining a first radial gap therebetween, and an outer surface of the liner and the second inner surface of the dome defining a second radial gap therebetween;
at least one mounting assembly configured to secure the liner to the dome, the at least one mounting assembly comprising:
a grommet arranged in the liner opening, the grommet including a grommet body extending axially through the liner opening between an inner surface of the liner and the outer surface of the liner, an inner collar extending radially outward from the grommet body and arranged in an inner groove defined along the inner surface of the liner, and an outer collar extending radially outward from the grommet body, axially opposite the inner collar, and arranged in an outer groove defined along the outer surface of the liner;
a bushing arranged in the liner opening and within the grommet, the grommet being arranged to reduce wear on the forward end of the liner by slidably engaging the bushing as the liner moves relative to the dome;
a pin received by the bushing and extending through the dome and the liner opening; and
a nut disposed adjacent the dome and configured to engage the pin;
wherein the grommet body, the inner collar, and the outer collar each contacts the liner.
2. The combustor assembly of claim 1 , wherein the radial interface surface is a machined surface to define the axial gap.
3. The combustor assembly of claim 1 , wherein the axial interface surface is a machined surface to define the first radial gap.
4. The combustor assembly of claim 1 , wherein the axial gap and the first radial gap are configured to allow a predetermined amount of airflow therethrough into the combustion chamber.
5. The combustor assembly of claim 1 , the dome further comprising a yoke and a base plate, wherein the second inner surface of the dome is an inner surface of the yoke, and wherein the outer collar is positioned between the outer surface of the liner and the inner surface of the yoke, and the inner collar is positioned between the inner surface of the liner and the base plate.
6. The combustor assembly of claim 1 , wherein the dome is formed of a metal material.
7. The combustor assembly of claim 1 , wherein the outer surface of the liner defines a cold side surface and a mid-span region, and wherein the liner defines an outer interface surface on the cold side surface within the mid-span region.
8. The combustor assembly of claim 1 , wherein the liner is an outer liner and wherein the dome is an outer dome section.
9. The combustor assembly of claim 1 , wherein the liner is an inner liner and wherein the dome is an inner dome section.
10. The combustor assembly of claim 1 , the dome further comprising a yoke and a base plate, wherein the pin extends through the yoke, the forward end of the liner, and the base plate.
11. The combustor assembly of claim 1 , wherein the axial interface surface is defined at a local area of the liner having an increased thickness relative to a first area immediately forward of the axial interface surface and a second area immediately aft of the axial interface surface.
12. The combustor assembly of claim 1 , wherein the axial interface surface and the first inner surface of the dome extend in a direction parallel to the axial direction.
13. The combustor assembly of claim 1 , wherein the radial interface surface and the forward surface of the dome extend in a direction parallel to the radial direction.
14. The combustor assembly of claim 1 , the dome comprising a yoke and a base plate, the yoke and the base plate defining the slot therebetween.
15. The combustor assembly of claim 14 , wherein the nut is configured to press the bushing between the yoke and the base plate.
16. The combustor assembly of claim 1 , wherein at least one of the axial gap or the first radial gap is less than about 0.150 inches during operating conditions of the combustor assembly.
17. The combustor assembly of claim 16 , wherein the first radial gap is less than about 0.020 inches during the operating conditions of the combustor assembly.
18. The combustor assembly of claim 17 , wherein the first radial gap is between 0.005 and 0.015 inches during the operating conditions of the combustor assembly.
19. The combustor assembly of claim 18 , wherein the axial gap is less than about 0.150 inches during the operating conditions of the combustor assembly.